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Working condition test device and control method for helicopter tail plane electric drive

A technology of test device and control method, which is applied in the direction of aircraft component testing, etc., can solve the problems of increasing test error, uncertainty, device cost, and inability to meet the working conditions, so as to avoid untrue loading, reduce quantity, and avoid axial The effect of being too long

Pending Publication Date: 2019-06-28
HEFEI UNIV OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, there are many types of reducer or motor test benches in China, most of which adopt the separation method of axial and radial loading of reducer / motor-axial loading-radial loading-torque loading, which increases the test error, Uncertainty and setup costs
At the same time, the step method is often used to adjust the load, which cannot meet the actual working conditions of the test.

Method used

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  • Working condition test device and control method for helicopter tail plane electric drive
  • Working condition test device and control method for helicopter tail plane electric drive
  • Working condition test device and control method for helicopter tail plane electric drive

Examples

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Embodiment Construction

[0031] In this example, if figure 1 As shown, a working condition test device for the electric drive of the helicopter empennage is connected to the encoder 3 by setting the first coupling 2 on the output shaft of the motor-reducer integrated machine 1, and the encoder 3 is connected to the axial direction through the stepped shaft 4. The radial loading integrated device 5 is connected; the axial radial loading integrated device 5 is connected with the angle sensor 7 through the second coupling 6; the angle sensor 7 is connected with the torque sensor 9 through the shaft 8; the torque sensor 9 is connected through the third coupling 10 is connected to the output shaft of the servo motor 11; here, the number of test devices is reduced by the axial and radial loading integrated device, and the error increase caused by the excessively long axial length of the test device is avoided; at the same time, it reflects the impact of the helicopter tail rotor when it is working. Focus on...

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Abstract

The invention discloses a working condition test device and control method for helicopter tail plane electric drive. A motor reducer integrated machine is used as a machine to be tested, and a pressure and torque load test is respectively achieved by an axial radial loading integrated device and a servo motor respectively; the axial radial loading integrated device integrates n independent loadingcylinders, and an axial loading plate is assembled with a loading box by a loading plate pulley and a spring. The device can simulate the real working conditions of a helicopter tail plane motor, thereby increasing the reliability of an experiment, reducing the energy consumption and improving the automation control performance.

Description

technical field [0001] The invention relates to the technical field of motor reducer tests, in particular to a working condition test device and a control method for electric drive of a helicopter empennage. Background technique [0002] Helicopters have always been an indispensable weapon in the military. With the development of modern military technology, the transmission system of helicopters has been transformed from traditional fuel engines to electric energy. At the same time, the continuous increase in people's livelihood needs has promoted the development of the aviation industry. Civilian helicopters, drones and other fields have broad application prospects, especially playing a key role in police activities, fire fighting, forest protection, and emergency rescue. The electric drive of the helicopter tail can increase the operating flexibility of the helicopter and improve the efficiency and reliability of the machine. Compared with the traditional mechanical tail r...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
Inventor 黄康马超赵韩孙浩杨磊
Owner HEFEI UNIV OF TECH